US7967239B2 - Rotor drive and control system for a high speed rotary wing aircraft - Google Patents

Rotor drive and control system for a high speed rotary wing aircraft Download PDF

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Publication number
US7967239B2
US7967239B2 US11/140,695 US14069505A US7967239B2 US 7967239 B2 US7967239 B2 US 7967239B2 US 14069505 A US14069505 A US 14069505A US 7967239 B2 US7967239 B2 US 7967239B2
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United States
Prior art keywords
main rotor
gearbox
recited
main
rotor system
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US11/140,695
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English (en)
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US20060269413A1 (en
Inventor
Bryan Saxon Cotton
Thomas L. Tully, JR.
Yuriy Z. Gmirya
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Sikorsky Aircraft Corp
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Sikorsky Aircraft Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by Sikorsky Aircraft Corp filed Critical Sikorsky Aircraft Corp
Assigned to SIKORSKY AIRCRAFT CORPORATION reassignment SIKORSKY AIRCRAFT CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: COTTON, BRYAN SAXON, GMIRYA, YURIY Z., TULLY JR., THOMAS L.
Priority to US11/140,695 priority Critical patent/US7967239B2/en
Priority to PCT/US2006/016640 priority patent/WO2007084171A2/fr
Priority to CN2006800190758A priority patent/CN101511676B/zh
Priority to EP06849296.6A priority patent/EP1893482B1/fr
Priority to RU2007148983/11A priority patent/RU2377161C2/ru
Priority to JP2008514657A priority patent/JP4727724B2/ja
Priority to CA2609943A priority patent/CA2609943C/fr
Publication of US20060269413A1 publication Critical patent/US20060269413A1/en
Priority to IL187765A priority patent/IL187765A/en
Publication of US7967239B2 publication Critical patent/US7967239B2/en
Application granted granted Critical
Expired - Fee Related legal-status Critical Current
Adjusted expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B64C27/10—Helicopters with two or more rotors arranged coaxially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers

Definitions

  • the present invention relates to a rotary-wing aircraft, and more particularly to a drive arrangement for a high speed compound or coaxial contra-rotating rotor aircraft in which a translational propulsion system provides translational thrust while the main rotor system is operated at a reduced airspeed in a reverse airflow condition during high speed flight.
  • the forward airspeed of a conventional rotary wing aircraft is limited by a number of factors. Among these is the tendency of the retreating blade to stall at high forward airspeeds. As the forward airspeed increases, the airflow velocity across the retreating blade slows such that the blade may approach a stall condition. In contrast, the airflow velocity across the advancing blade increases with increasing forward speed. Dissymmetry of lift is thereby generated by forward movement of the helicopter.
  • This dissymmetry may create an unstable condition if lift is not equalized across the advancing and retreating sectors of the rotor disc.
  • blade flapping and feathering are utilized to generally equalize the lift.
  • a rotary wing aircraft with a coaxial contra-rotating rigid rotor system is capable of higher speeds compared to conventional single rotor helicopters due in part to the balance of lift between the advancing sides of the main rotor blades on the upper and lower rotor systems.
  • the retreating side of the rotor discs are also generally free from classic retreating blade stall that conventional single or tandem rotor helicopters may suffer from.
  • a compound or coaxial contra-rotating rigid rotor aircraft operates a system in autorotation with supplemental translational thrust being provided by turbojet engines.
  • the main rotor system In high speed flight, the main rotor system is unloaded from the main rotor drive engines (or turboshafts), and means for controlling rotor RPM is limited to adjusting collective pitch.
  • rotor RPM is preferably decreased to prevent the rotor blade tips on the advancing sides of the rotor discs from entering a supersonic region as the aircraft airspeed increases.
  • autorotation is a rotary wing flight condition where the force to turn the blades comes from airflow to the underside of the rotors.
  • the source of this airflow generally is from either the downward motion of an aircraft, such as would happen after engine failure, or forward motion of an aircraft, such as level flight in an autogiro.
  • a drive system for a high speed rotary-wing aircraft may include a dual, contra-rotating, coaxial rotor system and a translational thrust system to provide translational thrust generally parallel to an aircraft longitudinal axis while the rotor system is operating in an autorotative or reverse flow state during a high-speed forward flight profile.
  • a combiner gearbox in meshing engagement with a main gearbox is driven by one or more engines such that the main gearbox and the translational thrust system are driven therethrough.
  • the engine drives the combiner gearbox and the main gearbox through an overrunning clutch.
  • the drive system permits the RPMs of the main rotor system to be controlled by offloading torque to the translational thrust system. That is, torque generated by the main rotor system from autorotation during high speed flight is absorbed by the translational thrust system so that the advancing side of the main rotor blades does not reach supersonic speeds and the retreating side of the main rotor blades may be placed in flat pitch as a result of using low collective and differential lateral cyclic such that the negative lift on the retreating side is eliminated and the upward lift on the advancing side is reduced. Thus, reducing vibrations to the airframe.
  • the drive system is configured so that during engine failure, the pusher propeller of the translational thrust system is set to flat pitch otherwise the load imposed on the drive system would slow the rotor system and prevent an autorotative landing.
  • the present invention therefore provides a rotor drive and control system for a high speed rotary-wing aircraft which minimizes a major source of vibration and performance degradation.
  • FIGS. 1A-1B are general views of an exemplary rotary wing aircraft embodiment for use with the present invention
  • FIG. 2 is a block diagram of a drive system of the present invention
  • FIG. 3 is a schematic view of the main rotor dynamics of a coaxial counter rotating rotor system
  • FIG. 4 is a block diagram of a flight control system.
  • FIG. 1A-1B illustrates a vertical takeoff and landing (VTOL) high speed compound or coaxial contra-rotating rigid rotor aircraft (collectively rotary-wing aircraft) 10 having a dual, contra-rotating, coaxial main rotor system 12 , which rotates about a rotor axis of rotation A.
  • the aircraft 10 includes an airframe 14 which supports the dual, contra-rotating, coaxial main rotor system 12 as well as a translational thrust system 30 which provides translational thrust generally parallel to an aircraft longitudinal axis L while the main rotor system 12 is operating in an autorotative or reverse flow state during a high-speed forward flight profile. It should be understood that other aircraft configurations will benefit from the present invention.
  • the main rotor system 12 includes a first rotor system 16 and a second rotor system 18 each rotor system 16 , 18 includes a multiple of rotor blades 20 mounted to a rotor hub 22 , 24 .
  • the main rotor system 12 is driven by a main gearbox 26 .
  • the translational thrust system 30 may be any system known in the art including, but not limited to a tractor propeller, side mounted propellers, etc.
  • the translational thrust system 30 includes a pusher propeller 32 with a propeller rotational axis P oriented substantially horizontal and parallel to the aircraft longitudinal axis L to provide thrust for high-speed flight.
  • the pusher propeller 32 may be mounted within an aerodynamic cowling 34 mounted to the rear of the airframe 14 .
  • the translational thrust system 30 is preferably driven by the same main gearbox 26 which drives the rotor systems 16 , 18 .
  • the drive system 34 of the aircraft 10 is schematically illustrated.
  • the main gearbox 26 is mechanically connected to the main rotor system 12 and to the translational thrust system 30 so that the main rotor system 12 and the translational thrust system 30 are both driven by the main gearbox 26 .
  • the drive system 34 may further include a combiner gearbox 36 in meshing engagement with the main gearbox 26 .
  • the combiner gearbox 36 may be driven by one or more engines E.
  • the engines E drive the combiner gearbox 36 and thus the main gearbox 26 through a disconnecting mechanism, preferably, an overrunning clutch 38 .
  • the translational thrust system 30 preferably includes a drive shaft 40 which is driven by the combiner gearbox 36 . It should be understood that although the combiner gearbox 36 is schematically illustrated as a separate component, the combiner gearbox 36 may alternatively be incorporated directly into the main gearbox 26 .
  • This drive arrangement permits the RPMs of the rotor system 12 to be controlled so that the advancing sides of the main rotor blades do not reach supersonic speeds by offloading torque to the translational thrust system 30 . That is, torque generated by the main rotor system 12 during autorotation in a high speed flight profile is absorbed by the translational thrust system 30 .
  • This arrangement is possible because the translational thrust system 30 requires significantly more power during high speed flight than the main rotor system 12 generates while the main rotor system 12 is designed to absorb less horsepower than the translational thrust system 30 .
  • the main rotor system 12 absorbs approximately 400 horsepower
  • the translational thrust system 30 absorbs approximately 1200 horsepower during high speed flight.
  • the aircraft 10 is opposite from that of a conventional helicopter in which the main rotor is the primary recipient of horsepower in the case of a dual engine failure, the anti-torque tail rotor continues to rotate in a speed proportional to the main rotor to maintain yaw control during autorotation.
  • the translational thrust system 30 provides the ability to slow the main rotor system 12 with a mechanical link between the two.
  • Offloading power from the main rotor to the propeller reduces the main rotors' RPMs and therefore allows (Referring to FIG. 3 ), the retreating blade to be placed in flat pitch with low collective and differential lateral cyclic such that the negative lift on the retreating side is eliminated and the upward lift on the advancing side is reduced.
  • the advancing disc sectors generates reduced positive lift while the retreating disc sections general little to no positive lift variations of phase or magnitude between the upper and lower rotor systems 16 , 18 is thereby minimized which minimizes vibration propagation to the airframe. Minimization of vibration permits operations at higher airspeeds for prolonged time periods over conventional coaxial, contra-rotating systems.
  • the translational thrust system 30 operates to brake the overspeeding main rotor system 12 .
  • the overrunning clutch 38 is located in-between the one or more engines E and combiner gearbox 36 . This is significant since, during an engine failure, the pusher propeller 32 of the translational thrust system 30 must be set to a flat pitch otherwise the load imposed on the drive system 34 will slow the rotor system 12 and prevent an autorotative landing.
  • the pusher propeller 32 is preferably a variable pitch propeller controlled by a flight control system (illustrated schematically in FIG. 4 ) which operates to adjust the pitch of the pusher propeller 32 in response to predefined situations such as an engine failure and in response to transient overspeeding of the main rotor system 12 . That is, the variable pitch pusher propeller 32 provides additional fidelity for the off loading of torque from the rotor system 12 as well as refined rotor system 12 speed control.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Retarders (AREA)
  • Control Of Turbines (AREA)
  • Arrangement Of Transmissions (AREA)
US11/140,695 2005-05-31 2005-05-31 Rotor drive and control system for a high speed rotary wing aircraft Expired - Fee Related US7967239B2 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US11/140,695 US7967239B2 (en) 2005-05-31 2005-05-31 Rotor drive and control system for a high speed rotary wing aircraft
RU2007148983/11A RU2377161C2 (ru) 2005-05-31 2006-04-28 Система привода несущих винтов и управления ими для высокоскоростного винтокрылого летательного аппарата
CN2006800190758A CN101511676B (zh) 2005-05-31 2006-04-28 用于高速旋翼飞机的转子驱动和控制系统
EP06849296.6A EP1893482B1 (fr) 2005-05-31 2006-04-28 Système d'entraînement et de commande de rotor pour aéronef à voilure tournante à grande vitesse
PCT/US2006/016640 WO2007084171A2 (fr) 2005-05-31 2006-04-28 Système d'entraînement et de commande de rotor pour aéronef à voilure tournante à grande vitesse
JP2008514657A JP4727724B2 (ja) 2005-05-31 2006-04-28 高速回転翼航空機用のロータ駆動装置および制御システム
CA2609943A CA2609943C (fr) 2005-05-31 2006-04-28 Systeme d'entrainement et de commande de rotor pour aeronef a voilure tournante a grande vitesse
IL187765A IL187765A (en) 2005-05-31 2007-11-29 Move rotor and control system for high-speed rotating wing aircraft @ high

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/140,695 US7967239B2 (en) 2005-05-31 2005-05-31 Rotor drive and control system for a high speed rotary wing aircraft

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US20060269413A1 US20060269413A1 (en) 2006-11-30
US7967239B2 true US7967239B2 (en) 2011-06-28

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US (1) US7967239B2 (fr)
EP (1) EP1893482B1 (fr)
JP (1) JP4727724B2 (fr)
CN (1) CN101511676B (fr)
CA (1) CA2609943C (fr)
IL (1) IL187765A (fr)
RU (1) RU2377161C2 (fr)
WO (1) WO2007084171A2 (fr)

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US20110163199A1 (en) * 2008-05-30 2011-07-07 Giles Cardozo A flying machine comprising twin contra-rotating vertical axis propellers
US20110198440A1 (en) * 2008-07-24 2011-08-18 Airbus Operations Aircraft comprising at least one engine having counter-rotating rotors
US20120025011A1 (en) * 2010-07-27 2012-02-02 Thomas Hsueh Autogyro with pre-rotation
US20120138730A1 (en) * 2009-05-25 2012-06-07 Claude Annie Perrichon Stabilized safety gyroplane
US20130175385A1 (en) * 2011-07-12 2013-07-11 Eurocopter Method of automatically controlling a rotary wing aircraft having at least one propulsion propeller, an autopilot device, and an aircraft
US20140154084A1 (en) * 2012-11-30 2014-06-05 Mark R. Alber Non-uniform blade distribution for rotary wing aircraft
US20150102158A1 (en) * 2013-10-15 2015-04-16 Sikorsky Aircraft Corporation Coaxial Rotor Yaw Control
US20150198436A1 (en) * 2014-01-16 2015-07-16 Sikorsky Aircraft Corporation Tip clearance measurement
US9120567B2 (en) 2012-06-11 2015-09-01 Sikorsky Aircraft Corporation High speed compound rotary wing aircraft
CN105314104A (zh) * 2015-11-20 2016-02-10 黑龙江科技大学 一种多旋翼飞行器内齿环动力传动系统
US20160083076A1 (en) * 2014-05-01 2016-03-24 Sikorsky Aircraft Corporation Automatic propeller torque protection system
WO2016053774A1 (fr) * 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Aéronef à voilure tournante, à double rotor
WO2016053997A1 (fr) * 2014-09-30 2016-04-07 Sikorsky Aircraft Corporation Configuration de giravion et procédé de conception de giravion
WO2016126304A1 (fr) * 2015-02-04 2016-08-11 Sikorsky Aircraft Corporation Commande de direction améliorée pour engin à voilure rotative coaxiale
US9505492B2 (en) 2012-02-23 2016-11-29 Sikorsky Aircraft Corporation Mission adaptive rotor blade
US10822076B2 (en) 2014-10-01 2020-11-03 Sikorsky Aircraft Corporation Dual rotor, rotary wing aircraft

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US6886777B2 (en) * 2001-02-14 2005-05-03 Airscooter Corporation Coaxial helicopter
US7758310B2 (en) * 2007-01-15 2010-07-20 Sikorsky Aircraft Corporation Translational thrust system for a rotary wing aircraft
US8167233B2 (en) * 2007-12-21 2012-05-01 Avx Aircraft Company Coaxial rotor aircraft
CN101618763A (zh) * 2008-07-02 2010-01-06 孙为红 微型高速直升自旋翼飞行器
WO2011018559A2 (fr) * 2009-08-14 2011-02-17 Claude Annie Perrichon Autogyre securise stabilise
DE102009040278B4 (de) * 2009-09-04 2013-08-01 Otmar Birkner Tragschrauber
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CA2874341C (fr) * 2012-05-21 2021-05-25 Paul E. Arlton Vehicule a ailes tournantes
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US9835093B2 (en) * 2013-09-19 2017-12-05 The Boeing Company Contra-rotating open fan propulsion system
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CN104097769A (zh) * 2014-06-27 2014-10-15 天津三爻航空航天科技发展有限公司 直升机旋翼头大桨夹持装置
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EP3186146B1 (fr) * 2014-08-28 2019-10-09 Sikorsky Aircraft Corporation Système de commande de pas
US10676184B2 (en) 2014-08-28 2020-06-09 Sikorsky Aircraft Corporation Pitch control system for an aircraft
EP3201080A4 (fr) 2014-10-01 2018-05-23 Sikorsky Aircraft Corporation Carénage de moyeu et d'arbre étanche pour aéronef à voilure tournante
WO2016054147A1 (fr) * 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Gestion de puissance entre un propulseur et un rotor coaxial d'un hélicoptère
RU2629635C2 (ru) * 2015-02-25 2017-08-30 Андрей Леонидович Шпади Движительная система высокоскоростного винтокрылого летательного аппарата (варианты)
CN104691752B (zh) * 2015-03-05 2016-04-27 葛讯 一种共轴高速直驱直升机及其飞行操纵方式
CN104875899B (zh) * 2015-04-03 2017-04-05 西北工业大学 一种可停转旋翼飞行器驱动系统以及改变其旋翼系统工作状态的方法
US10858116B2 (en) * 2018-09-04 2020-12-08 Textron Innovations Inc. Pusher rotorcraft drivetrain
RU2721028C1 (ru) * 2019-03-15 2020-05-15 Публичное акционерное общество "Казанский вертолётный завод" (ПАО "Казанский вертолётный завод") Способ посадки вертолёта в режиме авторотации
US11433093B2 (en) * 2019-08-01 2022-09-06 John Stevens George Compact gyroplane employing torque compensated main rotor and hybrid power train
US11572155B2 (en) * 2019-10-28 2023-02-07 Textron Innovations Inc. Rotorcraft having propeller generated power during autorotations
FR3107252A1 (fr) 2020-02-18 2021-08-20 Airbus Helicopters Procédé de commande d’un hélicoptère hybride lors d’une panne d’une installation motrice
CN112591114B (zh) * 2021-03-03 2021-07-16 北京清航紫荆装备科技有限公司 交叉双旋翼无人直升机及其动力系统
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US8727266B2 (en) 2008-05-30 2014-05-20 Gilo Industries Limited Flying machine comprising twin contra-rotating vertical axis propellers
US20110163199A1 (en) * 2008-05-30 2011-07-07 Giles Cardozo A flying machine comprising twin contra-rotating vertical axis propellers
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CN101511676A (zh) 2009-08-19
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JP4727724B2 (ja) 2011-07-20
WO2007084171A3 (fr) 2009-04-16
EP1893482A2 (fr) 2008-03-05
IL187765A (en) 2013-07-31
IL187765A0 (en) 2008-08-07
EP1893482A4 (fr) 2013-04-10
US20060269413A1 (en) 2006-11-30
EP1893482B1 (fr) 2014-07-02
JP2008545580A (ja) 2008-12-18
CA2609943C (fr) 2011-07-19
RU2007148983A (ru) 2009-07-10
RU2377161C2 (ru) 2009-12-27
WO2007084171A2 (fr) 2007-07-26

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